ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • AERODYNAMICS  (74)
  • Biology
  • COMPUTERS
  • Crustal deformation (cf. Earthquake precursor: deformation or strain)
  • GENERAL
  • unknown
  • 1975-1979  (73)
  • 1955-1959  (27)
  • 1978  (73)
  • 1958  (27)
Collection
Keywords
Years
  • 1975-1979  (73)
  • 1955-1959  (27)
Year
  • 1
    facet.materialart.
    Unknown
    Steady and unsteady transonic flow (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation of the transonic flow over a circular arc airfoil was conducted to obtain basic information for turbulence modeling of shock-induced separated flows and to verify numerical computer codes which are being developed to simulate such flows. The investigation included the employment of a laser velocimeter to obtain data concerning the mean velocity, the shear stress, and the turbulent kinetic energy profiles in the flowfield downstream of the airfoil midchord where the flow features are more complex. Depending on the free-stream Mach number, the flowfield developed was either steady with shock-wave-induced separation extending from the foot of the shock wave to beyond the trailing edge or unsteady with a periodic motion also undergoing shock-induced separation. The experimental data were compared with the results of numerical simulations in which a computer code was employed that solved the time-dependent Reynolds' averaged compressible Navier-Stokes equations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-160 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Aerodynamic heating of hypersonic configurations (1958)
    In:  CASI
    Details
    Publication Date: 2005-01-20
    Keywords: unknown
    Type: NACA CONF. ON HIGH-SPEED AERODYN. 1958; P 357-371
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Aerodynamic characteristics at Mach 6 of a wing-body concept for a hypersonic research airplane (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static aerodynamic characteristics of a 1/30 scale model of a wing-body concept for a high speed research airplane were investigated in the Langley 20 inch Mach six tunnel. The investigation consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was six at a Reynolds number, based on model fuselage length, of about 13,700,000. The test angle-of-attack range was 4 to 20 D at constant angles of sideslip of 0, 2, and 4 deg. The elevons were deflected from 10 to -15 D for pitch control. Roll and yaw control were investigated. Experimental aerodynamic characteristics are compared with analytical elements.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1249 , L-12183
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aerodynamic characteristics of a model using a vectored-over-wing powered lift concept. The effects of spanwise nozzle throat area, internal and external nozzle geometry, and vertical and axial location were investigated. These effects were studied at a Mach number of 0.186 over an angle-of-attack range from 14 deg to 40 deg. A high pressure air system was used to provide jet-exhaust simulation. Engine nozzle pressure ratio was varied from 1.0 (jet off) to approximately 3.75.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1215 , L-12015
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Index for aerodynamic data from the Bumblebee program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Bumblebee program, was designed to provide a supersonic guided missile. The aerodynamics program included a fundamental research effort in supersonic aerodynamics as well as a design task in developing both test vehicles and prototypes of tactical missiles. An index of aerodynamic missile data developed in this program is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145347
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Numerical computation of transonic flows by finite-element and finite-difference methods (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Studies on applications of the finite element approach to transonic flow calculations are reported. Different discretization techniques of the differential equations and boundary conditions are compared. Finite element analogs of Murman's mixed type finite difference operators for small disturbance formulations were constructed and the time dependent approach (using finite differences in time and finite elements in space) was examined.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3070
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Space shuttle afterbody aerodynamics/plume simulation data summary (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of parametric wind tunnel tests was conducted to provide a base for developing a simulation of afterbody/base aerodynamics for multibody/multibase rocket-powered vehicles (such as Space Shuttle) which use unheated air as the simulant gas in development wind tunnel tests. The tests described were parameterized on external configuration, nozzle internal configuration, base geometry, propulsion gas type, and freestream Mach number (0.5 to 3.5). The tests were conducted over a 4-year period. Presented in this report are the data and pertinent reference information necessary to perform an analysis which would lead to a simulation procedure. The type of data obtained during the tests described herein include model base afterbody, and nozzle internal surface static pressure distributions, model chamber pressure and temperature, and freestream conditions. Also included is a brief description of simulation procedures that were used by the Space Shuttle program.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1384 , M-276
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Application of shock tubes to transonic airfoil testing at high Reynolds numbers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynolds numbers of the order of 100 million can be produced, with limitations being imposed by the structural integrity of the facility or the model. A study of flow development over a simple circular arc airfoil at zero angle of attack was carried out in a shock tube at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photography and airfoil pressure measurements show that steady transonic flows similar to those produced for the same airfoil in a wind tunnel can be generated within the available testing time in a shock tube with properly contoured test section walls.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1268 , A-6855
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    Investigation of the stress-concentration mechanism for intraplate earthquakes (1978)
    In:  Geophysical Research Letters, Luxembourg, Conseil de l'Europe, vol. 5, no. March, pp. 477-479, pp. 2501, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1978
    Keywords: Stress ; Tectonics ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; GRL
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
  • 10
    facet.materialart.
    Unknown
    Displacement discontinuity in the elastic half-space (1958)
    In:  J. Appl. Mech., Oslo, Wiley, vol. 25, no. B10, pp. 125-128, pp. 2471, (ISSN: 1340-4202)
    Details
    Publication Date: 1958
    Keywords: Dislocation ; Crustal deformation (cf. Earthquake precursor: deformation or strain)
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY SEISMOLOGY
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...